CN117326113A - Unmanned aerial vehicle horn beta structure and unmanned aerial vehicle - Google Patents
Unmanned aerial vehicle horn beta structure and unmanned aerial vehicle Download PDFInfo
- Publication number
- CN117326113A CN117326113A CN202311629478.6A CN202311629478A CN117326113A CN 117326113 A CN117326113 A CN 117326113A CN 202311629478 A CN202311629478 A CN 202311629478A CN 117326113 A CN117326113 A CN 117326113A
- Authority
- CN
- China
- Prior art keywords
- telescopic rod
- horn
- unmanned aerial
- aerial vehicle
- fixedly connected
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Granted
Links
- 230000001681 protective effect Effects 0.000 claims description 15
- 229920000742 Cotton Polymers 0.000 claims description 6
- 230000009979 protective mechanism Effects 0.000 claims 3
- 230000000694 effects Effects 0.000 abstract description 6
- 239000003921 oil Substances 0.000 description 12
- 238000000034 method Methods 0.000 description 6
- 230000001105 regulatory effect Effects 0.000 description 6
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 238000001125 extrusion Methods 0.000 description 2
- 239000010720 hydraulic oil Substances 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
Classifications
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U30/00—Means for producing lift; Empennages; Arrangements thereof
- B64U30/20—Rotors; Rotor supports
- B64U30/29—Constructional aspects of rotors or rotor supports; Arrangements thereof
- B64U30/293—Foldable or collapsible rotors or rotor supports
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B64—AIRCRAFT; AVIATION; COSMONAUTICS
- B64U—UNMANNED AERIAL VEHICLES [UAV]; EQUIPMENT THEREFOR
- B64U20/00—Constructional aspects of UAVs
- B64U20/30—Constructional aspects of UAVs for safety, e.g. with frangible components
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/40—Weight reduction
Abstract
The application relates to unmanned aerial vehicle horn beta structure and unmanned aerial vehicle relates to unmanned aerial vehicle's technical field, and it includes the pivot, slidable mounting has the horn in the pivot, and the horn slides along the circumferencial direction of pivot, is provided with slip subassembly between horn and the pivot, is provided with clamping assembly in the pivot, and clamping assembly can make the horn fixed and swing perpendicularly jointly with the horn, and slip subassembly includes: the first limiting groove is formed in the side wall of the rotating shaft and is formed along the circumferential direction of the rotating shaft; the second limit groove is formed along the axial direction of the rotating shaft, and the first limit groove is communicated with the second limit groove; the sliding block is slidably mounted in the first limiting groove and fixedly connected with the horn, and can slide relatively with the second limiting groove, and the width of the sliding block is the same as that of the second limiting groove. The unmanned aerial vehicle has the effect of improving the flight stability of unmanned aerial vehicle when the external force is disturbed.
Description
Technical Field
The application relates to the technical field of unmanned aerial vehicles, in particular to an unmanned aerial vehicle horn folding structure and unmanned aerial vehicle.
Background
The unmanned aerial vehicle horn folding structure means that the horn on the unmanned aerial vehicle fuselage can realize folding and expansion's function through certain mechanical design and control means. The design can enable the unmanned aerial vehicle to have smaller volume when not using the horn, is convenient to carry and store, and can be unfolded when the horn is required to be used, so that a larger working range and functions are provided.
Among the prior art, unmanned aerial vehicle horn beta structure often adopts rigid connection in the expansion, and rigid connection can provide higher rigidity and stability, makes the horn can keep stable gesture and structure at the during operation, but when facing the complex environment, adaptability is relatively poor. When external force interference is encountered, the flight stability of the unmanned aerial vehicle is susceptible to influence.
From the above, unmanned aerial vehicle among the prior art is when receiving external force interference, and flight stability is relatively poor.
Disclosure of Invention
In order to improve unmanned aerial vehicle's flight stability when facing external force interference, this application provides an unmanned aerial vehicle horn beta structure and unmanned aerial vehicle.
The application provides a pair of unmanned aerial vehicle horn beta structure and unmanned aerial vehicle adopts following technical scheme:
in a first aspect, the present application provides an unmanned aerial vehicle horn folding structure, adopts following technical scheme:
the utility model provides an unmanned aerial vehicle horn beta structure, includes the pivot, slidable mounting has the horn in the pivot, the horn is followed the circumferencial direction of pivot is slided, the horn with be provided with sliding component between the pivot, be provided with clamping component in the pivot, clamping component can make the horn is fixed and with the common perpendicular swing of horn, sliding component includes:
the first limiting groove is formed in the side wall of the rotating shaft and is formed in the circumferential direction of the rotating shaft;
the second limiting groove is formed along the axial direction of the rotating shaft, and the first limiting groove is communicated with the second limiting groove;
the sliding block is slidably mounted in the first limiting groove and fixedly connected with the horn, the sliding block can slide relative to the second limiting groove, and the width of the sliding block is the same as that of the second limiting groove.
Through adopting above-mentioned technical scheme, accomplished the folding to the horn to when unmanned aerial vehicle received external force interference in the flight, clamping assembly made the horn remove along the length direction of second spacing groove, made the horn have the ability of automatically regulated, improved unmanned aerial vehicle horn folding mechanism when the external force interference in the face of flight stability.
Optionally, the fixed end of the first telescopic rod is fixedly arranged on the width side wall of the second limit groove;
the second telescopic rod is fixedly arranged on the width side wall of the second limiting groove opposite to the first telescopic rod, the movable end of the first telescopic rod is opposite to the movable end of the second telescopic rod, and one end, close to the movable end, of the fixed end of the first telescopic rod is communicated with one end, close to the movable end, of the fixed end of the second telescopic rod;
the third telescopic rod is fixedly arranged on the rotating shaft, and one end of the fixed end of the third telescopic rod, which is far away from the movable end, is communicated with one end of the fixed end of the first telescopic rod, which is far away from the movable end, through a hose;
the first spring is fixedly arranged on the first telescopic rod, one end of the first spring is fixedly connected with the fixed end of the first telescopic rod, and the other end of the first spring is fixedly connected with the movable end of the first telescopic rod;
the second spring is fixedly arranged on the second telescopic rod, one end of the second spring is fixedly connected with the fixed end of the second telescopic rod, and the other end of the second spring is fixedly connected with the movable end of the second telescopic rod.
Through adopting above-mentioned technical scheme, unmanned aerial vehicle receives external force when disturbing at the flight in-process, under the elasticity effect of first spring and second spring, horn, first telescopic link expansion end, second telescopic link expansion end and sliding block move along the length direction of second spacing groove together for the horn has the ability of automatically regulated, improves unmanned aerial vehicle horn folding mechanism and when the external force is disturbed facing the flight stability.
Optionally, a positioning component is disposed in the second limiting groove, and the positioning component includes:
the mounting hole is formed in the side wall of the communication position of the second limit groove and the first limit groove;
the wedge block is slidably arranged in the mounting hole, one end of the wedge block, which is far away from the mounting hole, is hemispherical, and the hemispherical end of the wedge block is positioned outside the mounting hole;
one end of the third spring is fixedly connected with the bottom wall of the mounting hole, and the other end of the third spring is fixedly connected with one end of the wedge block, which is close to the mounting hole;
the clamping groove is formed in the side wall, which can be abutted against the side wall of the second limiting groove, of the sliding block, the hemispherical end of the wedge block can enter the clamping groove, and one end, close to the wedge block, of the clamping groove is flaring.
Through adopting above-mentioned technical scheme, can fix a position the slider at the horn at folding in-process, avoid the slider to appear the deviation in the position when removing to first spacing groove from the second spacing groove, improved unmanned aerial vehicle horn folding mechanism's use convenience.
Optionally, be provided with adjusting part on the first telescopic link, adjusting part is used for canceling to press from both sides tight to the sliding block, adjusting part includes:
the oil storage cavity is fixedly arranged on the side wall of the first telescopic rod, one end, close to the movable end, of the fixed end of the first telescopic rod is communicated with the oil storage cavity, and threads are formed on the inner wall of the oil storage cavity;
the adjusting block is in threaded connection with the inner wall of the oil storage cavity.
Through adopting above-mentioned technical scheme, realize pressing from both sides tightly and loosening the sliding block through the position of adjustment regulating block, improved unmanned aerial vehicle horn folding mechanism's simple operation nature.
Optionally, a connection assembly is provided between the adjusting block and the wedge, and the connection assembly includes:
one end of the rack is fixedly connected with one end of the wedge block, which is close to the mounting hole, and the length direction of the rack is along the sliding direction of the wedge block;
the gear is rotatably arranged on the rotating shaft and meshed with the rack;
the first bevel gear is rotatably arranged on the rotating shaft and is fixedly connected with the gear coaxially;
the fixed end of the fourth telescopic rod is fixedly connected with the adjusting block;
one end of the fourth spring is fixedly connected with the movable end of the fourth telescopic rod, and the other end of the fourth spring is fixedly connected with the fixed end of the fourth telescopic rod;
the second bevel gear is meshed with one end, far away from the fourth telescopic rod, of the first bevel gear, and the second bevel gear is coaxially and fixedly connected with the movable end of the fourth telescopic rod;
the magnetic block is fixedly arranged at one end, far away from the wedge block, of the clamping groove.
Through adopting above-mentioned technical scheme, the removal of voussoir has been driven through the removal of sliding block in the second spacing inslot to utilize the removal of voussoir to realize pressing from both sides tightly and loosening the sliding block, make the horn can be fixed and can be folded, improved unmanned aerial vehicle horn folding mechanism's simple operation nature.
Optionally, a tightening assembly is arranged on the third telescopic rod, and the tightening assembly is used for locking the movable end of the third telescopic rod.
Through adopting above-mentioned technical scheme, lock the third telescopic link expansion end for the fixed in position of first telescopic link expansion end, second telescopic link expansion end and sliding block has improved unmanned aerial vehicle horn folding mechanism's stability.
Optionally, the tightening assembly includes:
the fixed bushing is sleeved on the movable end of the third telescopic rod and fixedly connected with the fixed end of the third telescopic rod;
and the tightening nut is in threaded connection with the tightening bushing.
Through adopting above-mentioned technical scheme, will tightly fix the nut screw thread and install on tightly fixing the bush for relative fixation between third telescopic link expansion end and the stiff end has improved unmanned aerial vehicle horn folding mechanism's stability.
In a second aspect, the present application provides an unmanned aerial vehicle, which adopts the following technical scheme:
the utility model provides an unmanned aerial vehicle, includes unmanned aerial vehicle horn beta structure and fuselage, pivot fixed mounting is in on the fuselage lateral wall, the pivot axial is along fuselage thickness direction.
Through adopting above-mentioned technical scheme for unmanned aerial vehicle receives external force interference in the flight, the horn can be adjusted voluntarily, has improved the flight stability when unmanned aerial vehicle receives external force interference in the flight.
Optionally, a step is arranged on the side wall of the machine body, and the step is used for placing the horn after the horn is folded.
Through adopting above-mentioned technical scheme, can avoid the horn to form the arch on unmanned aerial vehicle lateral wall after folding, on the one hand reduced required space, on the other hand can play the guard action to the horn.
Optionally, be provided with protection machanism on the fuselage lateral wall, protection machanism is used for protection screw behind the horn is folding, protection machanism includes:
the section of the protective cover is a right angle, one end of the protective cover is hinged with the machine body, the other end of the protective cover is detachably and fixedly connected with the machine body, and the right angle of the protective cover faces the step;
compressed cotton which is fixedly arranged on one end of the protective cover, which is close to the step.
Through adopting above-mentioned technical scheme, compressed cotton receives the extrusion of screw and takes place deformation for the screw is fixed, prevents that the screw from taking place to collide with and causing the damage, has improved unmanned aerial vehicle's storage security.
In summary, the present application includes at least one of the following beneficial technical effects:
when the unmanned aerial vehicle is interfered by external force in the flight process, under the action of the elastic force of the first spring and the second spring, the horn, the first telescopic rod movable end, the second telescopic rod movable end and the sliding block move together along the length direction of the second limiting groove, so that the horn has the automatic adjusting capability, and the flight stability of the unmanned aerial vehicle horn folding mechanism when the unmanned aerial vehicle horn folding mechanism faces the external force interference is improved;
the movement of the sliding block in the second limiting groove drives the movement of the wedge block, and the clamping and loosening of the sliding block are realized by utilizing the movement of the wedge block, so that the horn can be fixed and folded, and the operation convenience of the unmanned aerial vehicle horn folding mechanism is improved;
during the folding process of the arm, the protective cover is turned up; after the folding of the arm is completed, the protective cover is put down. At this moment, compression cotton receives the pressurization of screw and takes place deformation for the screw is fixed, prevents that the screw from taking place to collide with and causing the damage, has improved unmanned aerial vehicle's storage security.
Drawings
FIG. 1 is a schematic structural view of embodiment 1 of the present application;
FIG. 2 is a structural cross-sectional view of embodiment 1 of the present application;
FIG. 3 is an enlarged view of embodiment 1 of the present application at A of FIG. 2;
fig. 4 is a schematic structural view of embodiment 2 of the present application.
Reference numerals illustrate:
1. a rotating shaft; 2. a horn; 3. a sliding assembly; 31. a first limit groove; 32. the second limit groove; 33. a sliding block; 4. a clamping assembly; 41. a first telescopic rod; 42. a second telescopic rod; 43. a third telescopic rod; 44. a first spring; 45. a second spring; 5. a positioning assembly; 51. a mounting hole; 52. wedge blocks; 53. a third spring; 54. a clamping groove; 6. an adjustment assembly; 61. an oil storage chamber; 62. an adjusting block; 7. a connection assembly; 71. a rack; 72. a gear; 73. a first bevel gear; 74. a fourth telescopic rod; 75. a fourth spring; 76. a second bevel gear; 77. a magnetic block; 8. a tightening assembly; 81. tightly fixing the bushing; 82. tightening a nut; 9. a body; 91. a step; 92. and a protective cover.
Detailed Description
The present application is described in further detail below in conjunction with figures 1-4.
Example 1
The embodiment of the application discloses unmanned aerial vehicle horn beta structure. Referring to fig. 1 and 2, the folding structure of the unmanned aerial vehicle horn comprises a rotating shaft 1, wherein a horn 2 is slidably arranged on the rotating shaft 1, the horn 2 slides along the circumferential direction of the rotating shaft 1, a sliding component 3 is arranged between the horn 2 and the rotating shaft 1, a clamping component 4 is arranged on the rotating shaft 1, and the clamping component 4 can enable the horn 2 to be fixed and swing vertically together with the horn; the sliding component 3 comprises a first limit groove 31, the first limit groove 31 is formed in the side wall of the rotating shaft 1, and the first limit groove 31 is formed along the circumferential direction of the rotating shaft 1; the device further comprises a second limit groove 32, the second limit groove 32 is formed along the axial direction of the rotating shaft 1, and the first limit groove 31 is communicated with the second limit groove 32; the sliding block 33 is slidably mounted in the first limiting groove 31, the sliding block 33 is fixedly connected with the arm 2, the sliding block 33 can slide in the second limiting groove 32, and the width of the sliding block 33 is the same as that of the second limiting groove 32.
When the arm 2 is in the folded state and needs to be unfolded, the arm 2 is rotated, so that the sliding block 33 slides in the first limiting groove 31. When the sliding block 33 slides to the position where the first limiting groove 31 is communicated with the second limiting groove 32, the arm 2 is fully unfolded, at this time, the clamping assembly 4 clamps the sliding block 33 so that the arm 2 is fixed, and the sliding block 33 enters the second limiting groove 32 by adjusting the clamping assembly 4, so that the fixation of the arm 2 is completed. When unmanned aerial vehicle receives external force interference in the flight, clamping assembly 4 makes horn 2 remove along the length direction of second spacing groove 32 for horn 2 has the ability of automatically regulated, improves unmanned aerial vehicle horn folding mechanism and when the external force interference in the face of flight stability.
Referring to fig. 2, the clamping assembly 4 includes a first telescopic rod 41, and a fixed end of the first telescopic rod 41 is fixedly mounted on a width side wall of the second limiting groove 32; a second telescopic rod 42 is fixedly arranged on the other width side wall of the second limiting groove 32, the movable end of the first telescopic rod 41 and the movable end of the second telescopic rod 42 are close to each other, and one end of the fixed end of the first telescopic rod 41 close to the movable end is communicated with one end of the fixed end of the second telescopic rod 42 close to the movable end; the rotating shaft 1 is fixedly provided with a third telescopic rod 43, and one end of the fixed end of the third telescopic rod 43, which is far away from the movable end, is communicated with one end of the fixed end of the first telescopic rod 41, which is far away from the movable end, through a hose; a first spring 44 is fixedly arranged in the first telescopic rod 41, one end of the first spring 44 is fixedly connected with the fixed end of the first telescopic rod 41, and the other end of the first spring 44 is fixedly connected with the movable end of the first telescopic rod 41; a second spring 45 is fixedly arranged in the second telescopic rod 42, one end of the second spring 45 is fixedly connected with the fixed end of the second telescopic rod 42, the other end of the second spring 45 is fixedly connected with the movable end of the second telescopic rod 42, hydraulic oil is filled in cavities communicated with the first telescopic rod 41 and the second telescopic rod 42, and hydraulic oil is filled in cavities communicated with the first telescopic rod 41 and the third telescopic rod 43.
In the initial state, the distance between the movable end of the first telescopic rod 41 and the movable end of the second telescopic rod 42 is the same as the thickness of the horn 2, and when the horn 2 rotates to enable the sliding block 33 to slide to the position where the first limiting groove 31 and the second limiting groove 32 are communicated, the sliding block 33 can be clamped by the movable end of the first telescopic rod 41 and the movable end of the second telescopic rod 42. Then, the movable end of the third telescopic link 43 is moved, and the slider 33 enters the second limiting groove 32 in a state clamped by the first telescopic link 41 and the second telescopic link 42, and then, the movable end of the third telescopic link 43 is limited. When unmanned aerial vehicle receives external force interference in the flight, under the elasticity effect of first spring 44 and second spring 45, horn 2, first telescopic link 41 expansion end, second telescopic link 42 expansion end and sliding block 33 move along the length direction of second spacing groove 32 together for horn 2 has the ability of automatically regulated, improves unmanned aerial vehicle horn folding mechanism's flight stability when facing external force interference.
Referring to fig. 2, a positioning assembly 5 is disposed in the second limiting groove 32, the positioning assembly 5 includes a mounting hole 51, and the mounting hole 51 is formed on a side wall of the position where the second limiting groove 32 communicates with the first limiting groove 31; a wedge block 52 is slidably arranged in the mounting hole 51, one end of the wedge block 52 away from the mounting hole 51 is hemispherical, and the hemispherical end of the wedge block 52 is positioned outside the mounting hole 51; a third spring 53 is fixedly connected to one end of the wedge block 52 close to the bottom wall of the mounting hole 51, and one end of the third spring 53 away from the wedge block 52 is fixedly connected with the bottom wall of the mounting hole 51; still include draw-in groove 54, the draw-in groove 54 is offered on the lateral wall that regulating block 62 can with second spacing groove 32 lateral wall butt, and the hemisphere end of voussoir 52 can get into in the draw-in groove 54, and the one end that the voussoir 52 is close to draw-in groove 54 is flaring form, and the fixed mounting has magnetic path 77 on the one end that the voussoir 52 kept away from draw-in groove 54.
When folding the arm 2, the sliding block 33 is moved to the position where the second limiting groove 32 is communicated with the first limiting groove 31, at this time, the hemispherical end of the wedge 52 enters into the clamping groove 54 to prevent the sliding block 33 from continuing to move in the second limiting groove 32, then the sliding block 33 is moved to the first limiting groove 31, and the sliding block 33 is continuously moved in the first limiting groove 31 in a direction away from the second limiting groove 32, so that the arm 2 is folded. The positioning assembly 5 can position the sliding block 33 in the folding process of the horn 2, so that the sliding block 33 is prevented from deviating from the position of the second limiting groove 32 when moving to the first limiting groove 31, and the using convenience of the unmanned aerial vehicle horn folding mechanism is improved.
Referring to fig. 2, an adjusting component 6 is disposed on the first telescopic rod 41, the adjusting component 6 is used for canceling the clamping of the sliding block 33, the adjusting component 6 includes an oil storage cavity 61, the oil storage cavity 61 is fixedly mounted on the side wall of the first telescopic rod 41, one end of the fixed end of the first telescopic rod 41, which is far away from the movable end, is communicated with the oil storage cavity 61, threads are formed on the inner wall of the oil storage cavity 61, and an adjusting block 62 is connected on the inner arm of the oil storage cavity 61 in a threaded manner.
When the sliding block 33 needs to be clamped, the adjusting block 62 is moved in a direction away from the first telescopic rod 41, the space in the cavity where the first telescopic rod 41 and the second telescopic rod 42 are communicated is increased, and oil in the end, close to the movable end, of the fixed end of the second telescopic rod 42 is sucked into the first telescopic rod 41, so that the movable end of the second telescopic rod 42 is moved in a direction close to the movable end of the first telescopic rod 41, and the sliding block 33 is clamped. When the sliding block 33 needs to be loosened, the adjusting block 62 is moved in the direction close to the first telescopic rod 41, the space in the cavity where the first telescopic rod 41 and the second telescopic rod 42 are communicated is reduced, and the oil inside the end, close to the movable end, of the fixed end of the first telescopic rod 41 is pushed into the second telescopic rod 42, so that the movable end of the second telescopic rod 42 is moved in the direction far away from the movable end of the first telescopic rod 41, and the sliding block 33 is loosened. The clamping and loosening of the sliding block 33 are realized by adjusting the position of the adjusting block 62, so that the operation convenience of the unmanned aerial vehicle arm folding mechanism is improved.
Referring to fig. 2, a connection assembly 7 is provided between the adjusting block 62 and the wedge 52, the connection assembly 7 includes a rack 71, one end of the rack 71 is fixedly connected with one end of the wedge 52 close to the mounting hole 51, the rack 71 is installed on the rotating shaft 1 in a penetrating and sliding manner, and the length direction of the rack 71 is along the sliding direction of the wedge 52; a gear 72 is rotatably arranged on the side wall of the rotating shaft 1, and the gear 72 is meshed with a rack 71; the gear 72 is coaxially and fixedly connected with a first bevel gear 73, and the first bevel gear 73 is rotatably arranged on the side wall of the rotating shaft 1; one end of the adjusting block 62, which is far away from the first telescopic rod 41, is fixedly connected with a fourth telescopic rod 74, a fourth spring 75 is sleeved on the fourth telescopic rod 74, one end of the fourth spring 75 is fixedly connected with the fixed end of the fourth telescopic rod 74, and the other end of the fourth spring 75 is fixedly connected with the movable end of the fourth telescopic rod 74; the fourth telescopic rod 74 is coaxially and fixedly connected with a second bevel gear 76, and the second bevel gear 76 is meshed with one end, far away from the fourth telescopic rod 74, of the first bevel gear 73; and further comprises a magnetic block 77, wherein the magnetic block 77 is fixedly arranged on one end of the clamping groove 54 away from the wedge block 52.
When the sliding block 33 moves to the position where the first limiting groove 31 and the second limiting groove 32 are communicated, the hemispherical end of the wedge block 52 enters the clamping groove 54, under the action of the magnetic force of the magnetic block 77, the wedge block 52 moves in a direction away from the mounting hole 51, the wedge block 52 moves to enable the rack 71 fixedly connected with the wedge block 52 to move, the rack 71 moves to drive the gear 72 to rotate, the gear 72 rotates to enable the first bevel gear 73 to rotate, the second bevel gear 76 meshed with the first bevel gear 73 also rotates with the gear, the second bevel gear 76 rotates to enable the adjusting block 62 fixedly connected with the second bevel gear 76 through the fourth telescopic rod 74 to move in a direction approaching to the first telescopic rod 41, and the sliding block 33 is loosened. When the sliding block 33 moves in the second limiting groove 32, the hemispherical end of the wedge block 52 is extruded by the sliding block 33 into the mounting hole 51, the movement of the wedge block 52 causes the rack 71 fixedly connected with the wedge block 52 to move, the rack 71 moves to drive the gear 72 to rotate, the gear 72 rotates to cause the first bevel gear 73 to rotate, the second bevel gear 76 meshed with the first bevel gear 73 also rotates with the first bevel gear 73, the second bevel gear 76 rotates to cause the adjusting block 62 fixedly connected with the second bevel gear 76 through the fourth telescopic rod 74 to move in a direction away from the first telescopic rod 41, and the sliding block 33 is clamped. The movement of the sliding block 33 in the second limiting groove 32 drives the movement of the wedge block 52, and the clamping and loosening of the sliding block 33 are realized by utilizing the movement of the wedge block 52, so that the horn 2 can be fixed and folded, and the operation convenience of the unmanned aerial vehicle horn folding mechanism is improved.
Referring to fig. 2 and 3, the third telescopic rod 43 is provided with a tightening assembly 8, and the tightening assembly 8 is used for locking the movable end of the third telescopic rod 43.
After the movable end of the first telescopic rod 41, the movable end of the second telescopic rod 42 and the sliding block 33 are moved to the proper positions by moving the movable end of the third telescopic rod 43, the movable end of the third telescopic rod 43 is locked, so that the positions of the movable end of the first telescopic rod 41, the movable end of the second telescopic rod 42 and the sliding block 33 are fixed, and the stability of the unmanned aerial vehicle arm folding mechanism is improved.
Referring to fig. 3, the tightening assembly 8 includes a tightening bushing 81, the tightening bushing 81 is sleeved on the movable end of the third telescopic rod 43, and the tightening bushing 81 is fixedly connected with the fixed end of the third telescopic rod 43; a tightening nut 82 is screwed to the tightening bushing 81.
When the tightening nut 82 is mounted on the tightening bushing 81 in a threaded manner, the movable end and the fixed end of the third telescopic rod 43 are relatively fixed, and at this time, the movable end of the first telescopic rod 41, the movable end of the second telescopic rod 42 and the sliding block 33 cannot be displaced through the third telescopic rod 43, so that the stability of the unmanned aerial vehicle arm folding mechanism is improved.
The implementation principle of the unmanned aerial vehicle horn folding structure of the embodiment of the application is as follows: when the arm 2 needs to be unfolded, the arm 2 is rotated, so that the sliding block 33 slides from the first limiting groove 31 to a position where the first limiting groove 31 and the second limiting groove 32 are communicated, and at this time, the sliding block 33 is located between the movable end of the first telescopic rod 41 and the movable end of the second telescopic rod 42. Meanwhile, the hemispherical end of the wedge block 52 enters the clamping groove 54, the wedge block 52 moves away from the mounting hole 51 under the action of the magnetic force of the magnetic block 77, the movement of the wedge block 52 enables the rack 71 fixedly connected with the wedge block 52 to move, the rack 71 moves to drive the gear 72 to rotate, the gear 72 rotates to enable the first bevel gear 73 to rotate, the second bevel gear 76 meshed with the first bevel gear 73 also rotates with the rotation of the gear 72, the second bevel gear 76 rotates to enable the adjusting block 62 fixedly connected with the second bevel gear 76 through the fourth telescopic rod 74 to move towards the direction approaching to the first telescopic rod 41, and the sliding block 33 is loosened. And then the movable end of the third telescopic rod 43 is pushed so that the sliding block 33 enters the second limiting groove 32. In the process of moving the sliding block 33, the magnetic block 77 is separated from the wedge block 52, the wedge block 52 is extruded by the sliding block 33 into the mounting hole 51, the movement of the wedge block 52 enables the rack 71 fixedly connected with the wedge block 52 to move, the rack 71 moves to drive the gear 72 to rotate, the gear 72 rotates to enable the first bevel gear 73 to rotate, the second bevel gear 76 meshed with the first bevel gear 73 also rotates along with the rotation of the first bevel gear, the second bevel gear 76 rotates to enable the adjusting block 62 fixedly connected with the second bevel gear 76 through the fourth telescopic rod 74 to move in a direction away from the first telescopic rod 41, the sliding block 33 is clamped, and the fixing of the sliding block 33 and the arm 2 fixedly connected with the sliding block 33 is completed. When the unmanned aerial vehicle receives external force effect during the flight, the first telescopic link 41 and the second telescopic link 42 take place the same direction displacement with the sliding block 33 under external force impact, can reset under the effect of first spring 44 and second spring 45 after the impact is absorbed, make horn 2 possess the ability of receiving automatic adjustment when external force impact, improved unmanned aerial vehicle horn folding mechanism's flight stability when facing external force interference.
Example 2
The embodiment of the application discloses an unmanned aerial vehicle.
Referring to fig. 4, an unmanned aerial vehicle comprises an unmanned aerial vehicle arm folding mechanism and a fuselage 9, a rotating shaft 1 is fixedly installed on the side wall of the fuselage 9, and the rotating shaft 1 is axially along the thickness direction of the fuselage 9.
Through with unmanned aerial vehicle horn folding mechanism fixed mounting on unmanned aerial vehicle fuselage 9 lateral wall for unmanned aerial vehicle receives external force when disturbing in the flight, horn 2 can adjust voluntarily, has improved unmanned aerial vehicle and has received the flight stability when external force disturbed in the flight.
Referring to fig. 4, a step 91 is provided on a side wall of the body 9, and the step 91 is used for placing the horn 2 after the horn 2 is folded.
Through setting up step 91 and placing horn 2, can avoid horn 2 to form the arch on unmanned aerial vehicle lateral wall after folding, on the one hand reduced required space, on the other hand can play the guard action to horn 2.
Referring to fig. 4, a protection mechanism is arranged on the side wall of the machine body 9, the protection mechanism is used for protecting the propeller after the horn 2 is folded, the protection mechanism comprises a protection cover 92, the section of the protection cover 92 is a right angle, one end of the protection cover 92 is hinged with the machine body 9, the other end of the protection cover 92 is detachably and fixedly connected with the machine body 9, and the right angle of the protection cover 92 faces to the step 91; the protecting cover 92 is fixedly installed with compressed cotton at one end near the step 91.
During folding of the arm 2, the protective cover 92 is turned up; after the folding of the horn 2 is completed, the protective cover 92 is put down. At this moment, compression cotton receives the extrusion of screw and takes place deformation for the screw is fixed, prevents that the screw from taking place to collide with and causing the damage, has improved unmanned aerial vehicle's storage security.
The foregoing are all preferred embodiments of the present application, and are not intended to limit the scope of the present application in any way, therefore: all equivalent changes in structure, shape and principle of this application should be covered in the protection scope of this application.
Claims (10)
1. Unmanned aerial vehicle horn beta structure, its characterized in that: including pivot (1), slidable mounting has horn (2) in pivot (1), horn (2) are followed the circumferencial direction of pivot (1) is slided, horn (2) with be provided with slip subassembly (3) between pivot (1), be provided with clamping assembly (4) in pivot (1), clamping assembly (4) can make horn (2) are fixed and with common perpendicular swing of horn (2), slip subassembly (3) include:
the first limiting groove (31) is formed in the side wall of the rotating shaft (1), and the first limiting groove (31) is formed in the circumferential direction of the rotating shaft (1);
the second limiting groove (32) is formed in the axial direction of the rotating shaft (1), and the first limiting groove (31) is communicated with the second limiting groove (32);
the sliding block (33), sliding block (33) slidable mounting is in first spacing groove (31), sliding block (33) with horn (2) fixed connection, sliding block (33) can with second spacing groove (32) relative slip, sliding block (33) width with second spacing groove (32) width is the same.
2. The unmanned aerial vehicle horn folding structure according to claim 1, wherein the clamping assembly (4) comprises:
the fixed end of the first telescopic rod (41) is fixedly arranged on the width side wall of the second limit groove (32);
the second telescopic rod (42), the fixed end of the second telescopic rod (42) is fixedly arranged on the width side wall of the second limit groove (32) opposite to the first telescopic rod (41), the movable end of the first telescopic rod (41) is opposite to the movable end of the second telescopic rod (42), and one end, close to the movable end, of the fixed end of the first telescopic rod (41) is communicated with one end, close to the movable end, of the fixed end of the second telescopic rod (42);
the third telescopic rod (43), the said third telescopic rod (43) is fixedly mounted on said spindle (1), the one end far away from movable end of the said third telescopic rod (43) is communicated with one end far away from movable end of the said first telescopic rod (41) fixed end through the hose;
the first spring (44), the first spring (44) is fixedly mounted on the first telescopic rod (41), one end of the first spring (44) is fixedly connected with the fixed end of the first telescopic rod (41), and the other end of the first spring (44) is fixedly connected with the movable end of the first telescopic rod (41);
the second spring (45), second spring (45) fixed mounting is in on second telescopic link (42), the one end of second spring (45) with second telescopic link (42) stiff end fixed connection, the other end of second spring (45) with second telescopic link (42) expansion end fixed connection.
3. The unmanned aerial vehicle horn folding structure according to claim 2, wherein a positioning assembly (5) is provided in the second limiting groove (32), the positioning assembly (5) comprising:
the mounting hole (51) is formed in the side wall of the communication position of the second limit groove (32) and the first limit groove (31);
the wedge block (52) is slidably arranged in the mounting hole (51), one end of the wedge block (52) away from the mounting hole (51) is hemispherical, and the hemispherical end of the wedge block (52) is positioned outside the mounting hole (51);
one end of the third spring (53) is fixedly connected with the bottom wall of the mounting hole (51), and the other end of the third spring (53) is fixedly connected with one end of the wedge block (52) close to the mounting hole (51);
the clamping groove (54) is formed in the side wall, which can be abutted to the side wall of the second limiting groove (32), of the sliding block (33), the hemispherical end of the wedge block (52) can enter the clamping groove (54), and one end, close to the wedge block (52), of the clamping groove (54) is flaring.
4. A folding structure of an unmanned aerial vehicle horn according to claim 3, wherein: an adjusting component (6) is arranged on the first telescopic rod (41), the adjusting component (6) is used for canceling clamping of the sliding block (33), and the adjusting component (6) comprises:
the oil storage cavity (61), the oil storage cavity (61) is fixedly arranged on the side wall of the first telescopic rod (41), one end, close to the movable end, of the fixed end of the first telescopic rod (41) is communicated with the oil storage cavity (61), and threads are formed on the inner wall of the oil storage cavity (61);
and the adjusting block (62) is in threaded connection with the inner wall of the Chu Youqiang (61).
5. The unmanned aerial vehicle horn folding structure according to claim 4, wherein a connection assembly (7) is provided between the adjusting block (62) and the wedge (52), the connection assembly (7) comprising:
the rack (71), one end of the rack (71) is fixedly connected with one end of the wedge block (52) close to the mounting hole (51), and the length direction of the rack (71) is along the sliding direction of the wedge block (52);
a gear (72), the gear (72) is rotatably mounted on the rotating shaft (1), and the gear (72) is meshed with the rack (71);
the first bevel gear (73), the first bevel gear (73) is rotatably arranged on the rotating shaft (1), and the first bevel gear (73) is fixedly connected with the gear (72) in a coaxial way;
the fixed end of the fourth telescopic rod (74) is fixedly connected with the adjusting block (62);
one end of the fourth spring (75) is fixedly connected with the movable end of the fourth telescopic rod (74), and the other end of the fourth spring (75) is fixedly connected with the fixed end of the fourth telescopic rod (74);
the second bevel gear (76), the second bevel gear (76) is meshed with one end of the first bevel gear (73) far away from the fourth telescopic rod (74), and the second bevel gear (76) is fixedly connected with the movable end of the fourth telescopic rod (74) in a coaxial way;
the magnetic block (77) is fixedly arranged at one end of the clamping groove (54) far away from the wedge block (52).
6. The unmanned aerial vehicle horn folding structure of claim 2, wherein: the third telescopic rod (43) is provided with a fastening component (8), and the fastening component (8) is used for locking the movable end of the third telescopic rod (43).
7. The unmanned aerial vehicle horn folding structure of claim 6, wherein: the tightening assembly (8) comprises:
the tightening bushing (81) is sleeved on the movable end of the third telescopic rod (43), and the tightening bushing (81) is fixedly connected with the fixed end of the third telescopic rod (43);
-a tightening nut (82), said tightening nut (82) being in threaded connection with said tightening bushing (81).
8. An unmanned aerial vehicle, characterized by comprising the unmanned aerial vehicle horn folding structure and the fuselage of any one of claims 1-7, wherein the rotating shaft (1) is fixedly installed on the side wall of the fuselage (9), and the rotating shaft (1) is axially along the thickness direction of the fuselage (9).
9. The unmanned aerial vehicle according to claim 8, wherein a step (91) is provided on the side wall of the fuselage (9), the step (91) being used for placing the horn (2) after the horn (2) is folded.
10. The unmanned aerial vehicle according to claim 9, wherein a protective mechanism is provided on the side wall of the fuselage (9), the protective mechanism being for protecting the propeller after folding of the horn (2), the protective mechanism comprising:
the section of the protective cover (92) is a right angle, one end of the protective cover (92) is hinged with the machine body (9), the other end of the protective cover (92) is detachably and fixedly connected with the machine body (9), and the right angle of the protective cover (92) faces the step (91);
compressed cotton fixedly mounted on one end of the protective cover (92) close to the step (91).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311629478.6A CN117326113B (en) | 2023-12-01 | 2023-12-01 | Unmanned aerial vehicle horn beta structure and unmanned aerial vehicle |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202311629478.6A CN117326113B (en) | 2023-12-01 | 2023-12-01 | Unmanned aerial vehicle horn beta structure and unmanned aerial vehicle |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN117326113A true CN117326113A (en) | 2024-01-02 |
| CN117326113B CN117326113B (en) | 2024-02-02 |
Family
ID=89277757
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202311629478.6A Active CN117326113B (en) | 2023-12-01 | 2023-12-01 | Unmanned aerial vehicle horn beta structure and unmanned aerial vehicle |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN117326113B (en) |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020081202A1 (en) * | 2000-12-08 | 2002-06-27 | Nicolas Certain | Rotary-wing aircraft rotors with manually folding blades and electrical connection installation |
| CN206704516U (en) * | 2017-04-14 | 2017-12-05 | 深圳市世纪南方科技有限公司 | A kind of a variety of spacing horn fold mechanisms of unmanned plane |
| CN208319983U (en) * | 2018-06-04 | 2019-01-04 | 广东世季科技有限公司 | A kind of folding unmanned plane |
| WO2019144301A1 (en) * | 2018-01-23 | 2019-08-01 | 深圳市大疆创新科技有限公司 | Mechanical arm assembly and unmanned aerial vehicle |
-
2023
- 2023-12-01 CN CN202311629478.6A patent/CN117326113B/en active Active
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20020081202A1 (en) * | 2000-12-08 | 2002-06-27 | Nicolas Certain | Rotary-wing aircraft rotors with manually folding blades and electrical connection installation |
| CN206704516U (en) * | 2017-04-14 | 2017-12-05 | 深圳市世纪南方科技有限公司 | A kind of a variety of spacing horn fold mechanisms of unmanned plane |
| WO2019144301A1 (en) * | 2018-01-23 | 2019-08-01 | 深圳市大疆创新科技有限公司 | Mechanical arm assembly and unmanned aerial vehicle |
| CN208319983U (en) * | 2018-06-04 | 2019-01-04 | 广东世季科技有限公司 | A kind of folding unmanned plane |
Also Published As
| Publication number | Publication date |
|---|---|
| CN117326113B (en) | 2024-02-02 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| US4762038A (en) | Pipe machining apparatus | |
| CN107351062B (en) | Asymmetric over-constrained five-degree-of-freedom hybrid robot | |
| CN204912868U (en) | Foldable anti - countersink utensil | |
| CN117326113B (en) | Unmanned aerial vehicle horn beta structure and unmanned aerial vehicle | |
| CN113334098A (en) | High-speed five-axis machining center | |
| WO2011024717A1 (en) | Sunshade device | |
| CN109604640B (en) | Lathe for positioning and cutting | |
| CN102601392B (en) | Vertical lathe feeding knife rest | |
| CN203076976U (en) | Clamping mechanism of automatic circular sawing machine | |
| CN105382585A (en) | Clamping device with worm wheel and worm | |
| EP0826452A2 (en) | Turret with device for compensation of torque fluctuations | |
| CN110948112B (en) | Bearing ring outer wall burring device | |
| CN208451641U (en) | A kind of manipulator | |
| US4034647A (en) | Support for milling cutter | |
| CN106976432B (en) | Display device with automatic retraction function | |
| CN218976818U (en) | Rotary sound box | |
| CN219705244U (en) | Base assembly of intelligent robot | |
| CN210306744U (en) | Rotary machining head for watchcase machining machine tool | |
| CN109263774A (en) | A kind of environment protection architecture construction equipment has the Operation Van of monitoring function | |
| CN212322052U (en) | Coaxial stop device with adjustable screen | |
| CN220531972U (en) | Steel plate surface plastic spraying device | |
| CN219485036U (en) | Turning and milling composite numerical control lathe with power chuck and hydraulic turret | |
| CN215147322U (en) | Steel plate protective cover with opening and closing structure | |
| CN219008121U (en) | Unmanned aerial vehicle is protection casing for screw | |
| CN218819536U (en) | Safety monitoring device for machining positioning mechanism |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PB01 | Publication | ||
| PB01 | Publication | ||
| SE01 | Entry into force of request for substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant |